A major design consideration in helicopters is that of compensating for ssses on blades resulting from air forces during blade revolutions. Spinning rotor blades are severely stressed. To some degree conventional articulated helicopter rotor hubs overcome vibration difficulties, but high maintenance is a problem. Hingeless helicopter rotor assemblies, generally employing composite materials, were developed to overcome these obstacles. Such hingeless helicopter rotor assemblies usually include a rigid central hub member, and radial flexbeams rigidly attached to the hub member. Flexbeam rotors do not completely eliminate the dynamic instability difficulty. Even using these designs energy must be absorbed by damping means. The shear principle of damping is utilized in this invention.